Nova Patents
US7686582B2

Radial split serpentine microcircuits

Summary by NHIP

Radial split serpentine microcircuits

The turbine engine component features an airfoil with two distinct arrays of cooling microcircuits embedded on opposite sides of the mean line. Each array receives fluid via inlets containing a 90 degree bend, while a trailing edge circuit supplies the system through multiple holes and feed passages.

Claim Score by NHIP

Read claim 18, the broadest

Abstract

A turbine engine component, such as a turbine blade has an airfoil portion with an airfoil mean line, a pressure side, and a suction side. A first region on the pressure side of the airfoil portion has a first array of cooling microcircuits embedded in a wall forming the pressure side. A second region on the pressure side has a second array of cooling microcircuits embedded in the wall. The first region is located on a first side of the mean line and the second region is located on a second side of the mean line.

US7686582B2, drawing sheet 1
Sheet 1 of 5

Term

Projected expiry 2 July 2028.

  1. Priority and filed
  2. Granted
  3. Today
  4. Projected expiry

19 claims: 4 independent, 15 dependent

  1. 1
    A turbine engine component comprising:an airfoil portion having an airfoil mean line, a pressure side, and a suction side;a first region on said pressure side having a first array of cooling microcircuits embedded in a wall forming said pressure side;a second region on said pressure side having a second array of cooling microcircuits embedded in said wall;and said first region being located on a first side of said mean line and said second region being located on a second side of said mean line;a trailing edge internal circuit within said airfoil portion;said first array having a first cooling circuit with a first inlet located on said first side of said mean line, said first inlet receiving cooling fluid from said trailing edge internal circuit;said second array having a second cooling circuit with a second inlet located on said second side of said mean line, said second inlet receiving cooling fluid from said trailing edge internal circuit;and said trailing edge circuit having a plurality of holes for supplying fluid to a passageway having a plurality of openings to cool the trailing edge of the airfoil portion and a plurality of feed holes for supplying fluid to said first and second inlets.
  2. 15
    A turbine engine component comprising:an airfoil portion having an airfoil mean line, a pressure side, and a suction side;a first region on said pressure side having a first array of cooling microcircuits embedded in a wall forming said pressure side;a second region on said pressure side having a second array of cooling microcircuits embedded in said wall;and said first region being located on a first side of said mean line and said second region being located on a second side of said mean line;a trailing edge internal circuit within said airfoil portion;said first array having a first cooling circuit with a first inlet located on said first side of said mean line, said first inlet receiving cooling fluid from said trailing edge internal circuit;said second array having a second cooling circuit with a second inlet located on said second side of said mean line, said second inlet receiving cooling fluid from said trailing edge internal circuit, wherein said first cooling circuit has a first passageway and a second passageway at an angle with respect to said first passageway.
  3. 16
    A turbine engine component comprising:an airfoil portion having an airfoil mean line, a pressure side, and a suction side;a first region on said pressure side having a first array of cooling microcircuits embedded in a wall forming said pressure side;a second region on said pressure side having a second array of cooling microcircuits embedded in said wall;and said first region being located on a first side of said mean line and said second region being located on a second side of said mean line;a trailing edge internal circuit within said airfoil portion;said first array having a first cooling circuit with a first inlet located on said first side of said mean line, said first inlet receiving cooling fluid from said trailing edge internal circuit;said second array having a second cooling circuit with a second inlet located on said second side of said mean line, said second inlet receiving cooling fluid from said trailing edge internal circuit, wherein said second cooling circuit has a third passageway oriented along a span of said airfoil portion, a fourth passageway at an angle with respect to said third passageway, and a fifth passageway at an angle with respect to said fourth passageway.
  4. 18
    Broadest claimClaim Score 40, average(NHIP)A turbine engine component comprising:an airfoil portion having an airfoil mean line, a pressure side, and a suction side;a first region on said pressure side having a first array of cooling microcircuits embedded in a wall forming said pressure side;a second region on said pressure side having a second array of cooling microcircuits embedded in said wall;and said first region being located on a first side of said mean line and said second region being located on a second side of said mean line;a leading edge internal circuit;and said first array including a fourth cooling circuit having a fourth fluid inlet communicating with said leading edge internal circuit and a fifth cooling circuit having a fifth fluid inlet communicating with said leading edge internal circuit, wherein said fifth cooling circuit has a tenth cooling passageway communicating with said fifth fluid inlet and an eleventh cooling passageway communicating with said tenth cooling passageway and wherein said eleventh cooling passageway wraps around a leading edge of said airfoil portion.
Independent claims4